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Edging slender composite material airfoil and forming method thereof

A composite material and molding method technology, applied in other household appliances, household appliances, household components, etc., can solve the problems of easy deformation, low material utilization, high density, etc., to improve the interlayer performance and improve the interlayer performance. , the effect of increasing the fiber volume content

Active Publication Date: 2020-10-09
SHANGHAI COMPOSITES SCI & TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, for the slender wing structure mentioned in this article, the aluminum alloy material is the main material, and the use of this material to manufacture the slender wing surface has the disadvantages of easy deformation during processing, low material utilization rate and high density. and other shortcomings

Method used

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  • Edging slender composite material airfoil and forming method thereof
  • Edging slender composite material airfoil and forming method thereof
  • Edging slender composite material airfoil and forming method thereof

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Embodiment Construction

[0020] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0021] According to the molding method of a slender composite airfoil with side strips provided by the present invention, the airfoil is stitched and toughened in the Z direction after being laminated with carbon fiber UD cloth, and a prefabricated reinforcement based on an autoclave is used to inject resin into the prefabricated reinforcement and cure it. Autoclave / VARTM combined process molding.

[0022] Preferably, the airfoil is integrally formed by integral lamination, and the thickness and shape o...

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Abstract

The invention provides an edging slender composite material airfoil and forming method thereof. The edging slender composite material airfoil is subjected to ladder-like symmetrical overlaying with asection center through a carbon fiber UD cloth, after overlaying, Z-direction seaming is executed for toughening, and an autoclave / VARTM combined technology of injecting resin into a prefabricated reinforcement and curing based on the autoclave is used to realize forming. According to the invention, for the edging slender composite material airfoil, integral overlaying integrated forming is used,seaming for toughening is executed in overlaying Z direction, forming is realized through the autoclave / VARTM technology, a defect of relatively weaker interlayer performance of a product prepared through the conventional overlaying technology is made remedied, interlayer performance is improved, relatively higher fiber volume content and product forming quality are kept, and comprehensive performance of the composite material airfoil is guaranteed.

Description

technical field [0001] The invention relates to the technical field of composite material forming, in particular to a thin and long composite material airfoil and a forming method thereof. Background technique [0002] With the development of aerospace technology, the development trend of flying missiles includes characteristics such as long range, fast speed, and good maneuverability, which also determines that missiles must take the road of light weight. Composite materials have high specific modulus and specific strength, and the composite materialization of missile structures is one of the ways to reduce the weight of aviation missiles. As a part of the missile, the lightweight realization of the wings plays a positive role in reducing the weight of the aircraft, increasing the range and payload, and improving the maneuverability of the aircraft system. [0003] At present, relevant personnel have carried out more research on composite materials for smaller missile tail...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34B29C70/36B29C70/54B29L31/30
CPCB29C70/342B29C70/345B29C70/36B29C70/54B29L2031/3097
Inventor 梁燕民周涛吴鑫锐章宇界史文锋叶周军董斌杨赟左龙彦翟东坤
Owner SHANGHAI COMPOSITES SCI & TECH CO LTD
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